Thermal test fixture and test method for satellite-borne laser communication terminal

Abstract

The present invention provides a thermal test tool and test method for a satellite-borne laser communication terminal, comprising: a first heat flow simulation module, configured to directly apply heat flow to a bearing component of the satellite-borne laser communication terminal; a second heat flow simulation module, configured to indirectly apply heat flow to a filter of the satellite-borne laser communication terminal; and a support system, configured to support the satellite-borne laser communication terminal and the second heat flow simulation module, and to fix the first heat flow simulation module.

Description

Technical Field

[0001] The present invention relates to the field of aerospace technology, and in particular to a thermal test fixture and a test method for a satellite-borne laser communication terminal. Background Art

[0002] Satellite laser communication technology is a powerful means to achieve high-speed space communication, and can meet the huge demand for information transmission in current military and civilian dual-use communication technology. Compared with traditional microwave communication technology, laser communication has the advantages of high speed, confidentiality, anti-interference and miniaturization. However, due to the relatively small divergence angle of the laser beam, the long communication distance and the small receiving field of view of the target terminal, the aiming, capture and tracking accuracy have a great impact on the communication quality. A slight pointing deviation will cause the received energy to decrease and the bit error rate to increase. The deformation caused by the uneven temperature of optical components such as the main mirror of the laser communication terminal will cause large aiming errors and tracking errors.

[0003] Therefore, it is necessary to carry out a separate thermal control design for the laser communication terminal to ensure the temperature uniformity and stability during its on-orbit operation. In order to evaluate the effectiveness of the thermal control design, single-machine vacuum thermal test verification is particularly important. At present, vacuum thermal tests on optical payloads such as satellite-borne laser communication terminals are mostly focused on the exploration of two-dimensional turntables, and there are few experimental studies on the overall laser communication terminal. Summary of the invention

[0004] The purpose of the present invention is to provide a thermal test tool and test method for a satellite-borne laser communication terminal, so as to solve the problem that the existing laser communication terminal lacks accurate vacuum thermal test equipment.

[0005] In order to solve the above technical problems, the present invention provides a thermal test tool for a satellite-borne laser communication terminal, comprising:

[0006] A first heat flow simulation module is configured to directly apply heat flow to the bearing component of the satellite-borne laser communication terminal;

[0007] A second heat flow simulation module is configured to indirectly apply heat flow to the filter of the satellite-borne laser communication terminal; and

[0008] The support system is configured to support the satellite-borne laser communication terminal and the second heat flow simulation module, and to fix the first heat flow simulation module.

[0009] Optionally, in the thermal test fixture for the satellite-borne laser communication terminal, the support system includes a fixture plate and a support structure, wherein:

[0010] The tooling plate is horizontally fixed on the guide rail through a supporting structure;

[0011] The satellite-borne laser communication terminal is placed horizontally and fixed on the tooling plate;

[0012] A level adjustment device is provided between the tooling plate and the supporting structure for adjusting the levelness of the tooling plate.

[0013] Optionally, in the satellite-borne laser communication terminal thermal test fixture, the first heat flow simulation module includes a heating unit and a temperature measurement unit, wherein:

[0014] The heating unit is attached to the bottom surface of the tooling plate facing the guide rail, and the temperature measuring unit and the heating unit are arranged alternately;

[0015] A glass fiber reinforced plastic heat-insulating pad is provided between the tooling plate and the support structure to prevent the heat of the heating unit from leaking to the support structure through the tooling plate, and to prevent the heating unit from leaking electricity to the support structure through the tooling plate;

[0016] The heating unit and the temperature measuring unit maintain the interface temperature between the satellite-borne laser communication terminal and the mounting surface of the tooling plate.

[0017] Optionally, in the satellite-borne laser communication terminal thermal test fixture, the support system includes a transverse adjustment mounting hole and a support rod, wherein:

[0018] The lateral adjustment mounting hole is located on the tooling plate and corresponds to the position of the satellite-borne laser communication terminal;

[0019] The support rod passes through the transverse adjustment mounting hole and is fixed at the connection with the transverse adjustment mounting hole.

[0020] Optionally, in the satellite-borne laser communication terminal thermal test fixture, the second heat flow simulation module includes an infrared cage and a heat flow meter, wherein:

[0021] The infrared cage is fixed to the end rod of the support rod and faces the filter;

[0022] The heat flow meter is arranged on a side of the infrared cage facing away from the filter;

[0023] The end rod of the support rod has the functions of lateral and 360° rotation adjustment;

[0024] Both sides of the infrared cage resistance wire are coated with black paint to increase the surface infrared emissivity.

[0025] Optionally, in the above-mentioned thermal test fixture for the satellite-borne laser communication terminal, the support rod includes a longitudinal adjustment device, a heat flux meter adjustment device, and a lateral and rotational adjustment device, wherein:

[0026] The longitudinal adjustment device is used to adjust the support rod according to the height of the satellite-borne laser communication terminal;

[0027] The lateral and rotational adjustment device is used to adjust the infrared cage to align with the lens barrel of the satellite-borne laser communication terminal in a lateral position according to its direction, and then rotate it to a suitable angle so that the infrared cage is parallel to and directly faces the filter;

[0028] The heat flux meter adjustment device is used to adjust the position of the heat flux meter so that the distance between the heat flux meter and the filter is consistent with the distance between the heat flux meter and the infrared cage.

[0029] The present invention also provides a test method based on the above-mentioned thermal test tooling for a satellite-borne laser communication terminal.

[0030] The main structure of the satellite-borne laser communication terminal is subjected to contact heat flow simulation with the first heat flow simulation module. The surface of the satellite-borne laser communication terminal is wrapped with multi-layer components. A heating circuit is pasted on the inner surface of the outermost layer of the multi-layer components to simulate the heat flow outside the space. The simulation power is determined in combination with simulation analysis.

[0031] Optionally, in the thermal test method for the satellite-borne laser communication terminal, the optical filter of the satellite-borne laser communication terminal and the second heat flow simulation module perform non-contact heat flow simulation, and the heat flux density absorbed by the optical filter is determined in combination with simulation analysis;

[0032] Determine the distance between the second heat flow simulation module and the filter according to the heat flow density absorbed by the filter;

[0033] The relationship between the heat flux density applied by the second heat flux simulation module and the temperature of the heat flux meter is determined according to the distance between the second heat flux simulation module and the filter.

[0034] Optionally, in the above-mentioned thermal test method for the satellite-borne laser communication terminal, after the satellite-borne laser communication terminal is fixed on the tooling plate and the pointing position is adjusted, the longitudinal adjustment device, as well as the lateral and rotational adjustment devices are adjusted so that the infrared cage is parallel to the filter and adjusted to a set distance;

[0035] The heat flow meter adjustment device is adjusted so that the heat flow meters are arranged at equal distances on the back side of the infrared cage.

[0036] Optionally, in the thermal test method for the satellite-borne laser communication terminal, after the space simulation equipment meets the test requirements, the infrared cage is calibrated when other heat flow simulation methods are not turned on, and the closed-loop control temperature of the heat flux meter is set in combination with the simulation results, and the current applied to the infrared cage is recorded. When the test officially starts, a fixed current is used to control the infrared cage to apply the corresponding heat flux, so as to avoid deviations caused by the influence of the surrounding environment on the heat flux meter introduced by the closed-loop temperature control method of the heat flux meter.

[0037] In the thermal test fixture and test method for satellite-borne laser communication terminals provided by the present invention, heat flow is directly applied to the bearing components of the satellite-borne laser communication terminal through the first heat flow simulation module, and heat flow is indirectly applied to the filter of the satellite-borne laser communication terminal by the second heat flow simulation module. A simple, convenient and highly adaptable test fixture and heat flow simulation method are provided for optical loads such as satellite-borne laser communication terminals. The fixture can be quickly disassembled, put into tanks and adjust levels, and also has certain scalability.

[0038] Specifically, the new design of the infrared cage structure solves the difficulty of simulating the heat flow absorbed by the filter, improves the accuracy of the heat flow simulation in the thermal test of the laser communication terminal, and also provides a method for simulating the heat flow outside the lens of other optical payloads. BRIEF DESCRIPTION OF THE DRAWINGS

[0039] Figure 1 It is a schematic diagram of a thermal test tooling for a satellite-borne laser communication terminal according to an embodiment of the present invention;

[0040] Figure 2 It is a schematic diagram of an infrared cage and a support rod of a thermal test tooling for a satellite-borne laser communication terminal according to an embodiment of the present invention;

[0041] As shown in the figure:

[0042] 100-heat test tooling;

[0043] 110-guide rail;

[0044] 120-infrared cage and support rod;

[0045] 130- Satellite-borne laser communication terminal;

[0046] 140- tooling board;

[0047] 150- thermal insulation pad;

[0048] 160-Horizontal adjustment device;

[0049] 170-heating unit;

[0050] 180-temperature measuring unit;

[0051] 190-lateral adjustment mounting hole;

[0052] 200-infrared cage and support rod;

[0053] 210-support rod;

[0054] 220-longitudinal adjustment device;

[0055] 230-heat flow meter;

[0056] 240-infrared cage;

[0057] 250- Lateral and rotational adjustment. DETAILED DESCRIPTION

[0058] The following is a further detailed description of the thermal test fixture and test method of the satellite-borne laser communication terminal proposed by the present invention in conjunction with the accompanying drawings and specific embodiments. The advantages and features of the present invention will become clearer according to the following description and claims. It should be noted that the drawings are all in a very simplified form and are not in precise proportions, and are only used to conveniently and clearly assist in explaining the purpose of the embodiments of the present invention.

[0059] In addition, unless otherwise specified, the features in different embodiments of the present invention may be combined with each other. For example, a feature in the second embodiment may be used to replace a corresponding feature in the first embodiment or a feature with the same or similar function, and the resulting embodiment also falls within the disclosure or description scope of the present application.

[0060] The core idea of ​​the present invention is to provide a thermal test fixture and test method for a satellite-borne laser communication terminal to solve the problem that the existing laser communication terminal lacks accurate vacuum thermal test equipment.

[0061] The single-unit vacuum thermal test is one of the most important environmental tests in the development process of satellite units. Its purpose is to verify the rationality of the single-unit thermal design and to assess the unit's ability to withstand high and low temperatures and temperature changes under vacuum conditions, so as to expose and discover defects in the unit's materials, components and processes in advance. The accuracy of the single-unit vacuum thermal test is closely related to the accuracy of the application of external heat flux in space. The method of establishing a thermal model to determine the external heat flux in simulation software is relatively mature. The key lies in the method used for heat flux simulation. At present, there are two commonly used external heat flux simulation methods: contact and non-contact. The first is to directly paste a heating circuit on the surface of the structure or on the inner side of the outermost layer of the multi-layer component coated on the surface for heat flux simulation. This method can directly determine the heating circuit current according to the calculated power, which is convenient for application; the second is to arrange an infrared lamp array or infrared cage at a certain distance from the surface for heat flux simulation. This method requires the introduction of a heat flux meter to measure the heat flux density absorbed by the surface, which needs to be calibrated and corrected in the space environment simulation equipment after simulation calculation.

[0062] For satellite-borne laser communication terminals, the outermost part of the lens barrel is the filter, which has extremely high cleanliness requirements and is a translucent structure. It is impossible to stick a heater on its surface to simulate heat flow. Due to the limitations of size and structure of the infrared lamp array, the heat flow of the filter cannot meet the test uniformity requirements, and the heat flux meter placed under the infrared lamp will inevitably block part of the filter, resulting in a large simulation deviation. The heat flux meter of the infrared cage has similar problems. In addition, simulation analysis shows that the solar heat flux entering and absorbed through the lens filter cannot be ignored. Therefore, a thermal test fixture and heat flow simulation method that can adapt to optical loads such as laser communication terminals are needed.

[0063] To realize the above idea, the present invention provides a thermal test tool and test method for a satellite-borne laser communication terminal, including: a first heat flow simulation module, configured to directly apply heat flow to the bearing components of the satellite-borne laser communication terminal; a second heat flow simulation module, configured to indirectly apply heat flow to the filter of the satellite-borne laser communication terminal; and a support system, configured to support the satellite-borne laser communication terminal and the second heat flow simulation module, and to fix the first heat flow simulation module.

[0064] The present invention discloses a thermal test fixture 100 and a test method for a satellite-borne laser communication terminal, which is suitable for a vacuum thermal test of a satellite-borne laser communication terminal 130 in a space environment simulator to assess the rationality of its thermal design. It is mainly composed of a fixture plate 140, an infrared cage and a support rod 120. The satellite-borne laser communication terminal 130 is fixed on the fixture plate 140 with adjustable level, and a transverse adjustment mounting hole 190 is arranged on the fixture plate 140 for installing and adjusting the position of the infrared cage and the support rod 120 (including the infrared cage and the support rod). The infrared cage is fixed to the end rod of the support rod, and the corresponding angle and distance can be adjusted according to the direction of the lens barrel of the satellite-borne laser communication terminal 130. The present invention provides a simple, convenient and highly adaptable test tooling and heat flow simulation method for optical payloads such as the satellite-borne laser communication terminal 130. The tooling can be quickly disassembled and assembled, put into a tank and adjust the level, and also has certain scalability. The new design of the infrared cage structure solves the difficulty of simulating the heat flow absorbed by the filter, improves the accuracy of the heat flow simulation in the thermal test of the satellite-borne laser communication terminal 130, and also provides a method for simulating the heat flow outside the lens of other optical payloads.

[0065] like Figure 1 As shown, the satellite-borne laser communication terminal thermal test tool 100 provided by the present invention is mainly composed of a tooling plate 140, an infrared cage and a support rod 120. The satellite-borne laser communication terminal 130 is installed on the tooling plate 140, and the tooling plate 140 is fixed to the guide rail 110 through a supporting structure. The supporting structure and the tooling plate 140 are directly provided with a fiberglass thermal insulation pad 150 to ensure the thermal insulation and insulation performance between the two. The horizontal adjustment device 160 is used to adjust the horizontality of the tooling plate 140 to be better than 1mm / m. The infrared cage and the support rod 120 are fixed to the lateral adjustment mounting hole 190 of the tooling plate 140 according to the position of the satellite-borne laser communication terminal 130. The heating unit 170 and the temperature measuring unit 180 are arranged on the bottom surface of the tooling plate 140 to control the interface temperature between the satellite-borne laser communication terminal 130 and the mounting surface of the tooling plate 140.

[0066] Main structure of tooling board 140: A support structure is installed at the bottom of tooling board 140, and heating unit 170 and temperature measuring unit 180 are arranged on the bottom surface of tooling board 140 and used to set the interface temperature of tooling board 140; infrared cage and support rod: The infrared cage support rod is fixed to the transverse adjustment hole of tooling board 140, and has the function of adjusting the position in the transverse and longitudinal directions; the support structure has a horizontal adjustment function to ensure that the plane levelness of the tooling board 140 carrying the tested satellite laser communication terminal 130 is better than 1mm / m. The tooling board 140 and the support structure are heat-insulated and insulated. A glass fiber reinforced plastic heat-insulating pad 150 is provided on the contact surface between the support structure and the tooling board 140. One side of the tooling board 140 has a transverse adjustment installation hole 190. The bottom surface of the tooling board 140 is arranged with a heating and temperature measuring unit 180, which has the function of closed-loop control of the interface temperature of the tooling board 140. The infrared cage and support rod 120 have a longitudinal adjustment function. The end rod of the support rod has the functions of lateral and 360° rotation adjustment. In order to achieve a better temperature control effect, a plurality of temperature measuring sensors are arranged at the installation position of the satellite-borne laser communication terminal 130 .

[0067] Figure 2 The infrared cage and support rod 200 in the thermal test fixture 100 provided by the present invention. The support rod 210 can be installed by selecting a suitable lateral adjustment mounting hole according to the position of the satellite-borne laser communication terminal 130, and the longitudinal adjustment device 220 can adjust the position of the support rod according to the height of the satellite-borne laser communication terminal 130. The lateral and rotation adjustment device 250 first adjusts the lateral position of the infrared cage 240 according to the direction of the lens barrel of the satellite-borne laser communication terminal 130, and then rotates it to a suitable angle to make it parallel to the lens barrel filter. The infrared heat flow meter 230 is arranged on the back side of the infrared cage 240 and adjusted to a position consistent with the distance between the filter and the infrared cage.

[0068] The infrared cage heat flux meter 230 is arranged on the back side and has a longitudinal adjustment function. To ensure the measurement accuracy of the heat flux meter 230, the surfaces of both sides of the infrared cage resistance wire are coated with black paint, which has the function of simulating the heat flow outside the barrel space of the satellite-borne laser communication terminal 130. The infrared heat flux meter 230 is arranged on the back side of the infrared cage, and the distance between the heat flux meter 230 and the infrared cage is adjustable. The distance between the infrared heat flux meter 230 and the infrared cage is adjustable. The infrared cage is fixed to the end rod of the support rod and has the function of lateral and 360° rotation adjustment.

[0069] The main structure of the satellite-borne laser communication terminal 130 uses a contact heat flow simulation method. A heating circuit is pasted on the inner surface of the outermost layer of the multi-layer component to simulate the heat flow outside the space. The simulated power can be determined in combination with simulation analysis. The multi-layer component is composed of 15 layers of aluminum-coated polyester film and 15 layers of polyester mesh. The outermost layer of the multi-layer component is a layer of F46, and the heater is pasted on the inner surface of this layer.

[0070] The contact method cannot be used to simulate the heat flow of the filter in front of the lens barrel of the satellite-borne laser communication terminal 130, so a non-contact infrared cage is used for simulation. Combined with simulation analysis, the heat flux density absorbed by the filter is determined, and then the distance between the infrared cage and the filter and the relationship between the heat flux density applied by the infrared cage and the temperature of the heat flux meter 230 at this distance are determined, specifically including: the simulation analysis calculates the sum of the solar radiation heat flux, the earth's reflected heat flux and the earth's infrared radiation heat flux on each surface of the orbital laser terminal:

[0071] Q=Q1+Q2+Q3

[0072] Q is the external heat flux received by the surface of the satellite-borne laser communication terminal, Q1 is the direct solar radiation, Q2 is the external heat flux reflected by the earth, and Q3 is the heat flux of the earth's infrared radiation;

[0073]

[0074] S is the solar constant, a is the average albedo, A is the surface area, α is the surface solar absorptivity, ε is the surface infrared emissivity, φ1 is the solar radiation angular coefficient, φ2 is the earth albedo angular coefficient, and φ3 is the earth infrared angular coefficient;

[0075] For medium and high orbit satellites, the latter two items can be ignored. In particular, since the filter is semi-transparent, the heat flux passing through the filter will also be absorbed by the black surface with high absorption rate inside the lens barrel, and the calculation formula should take this part of the heat flux into account. Therefore, the formula can be simplified to

[0076] Q=S(α+τ)Aφ1

[0077] τ is the filter transmittance;

[0078] After the satellite-borne laser communication terminal 130 is fixed on the tooling plate 140 and the pointing position is adjusted, the infrared cage is parallel to the filter and adjusted to a set distance by adjusting the longitudinal and transverse positions and angles of the infrared cage support rods; the heat flux meter 230 is arranged at an equal distance on the back side of the infrared cage to reduce the blocking effect on the front filter;

[0079] After the space simulation equipment meets the test requirements, the infrared cage is calibrated when other heat flow simulation methods are not turned on. The closed-loop control temperature of the heat flow meter 230 is set in combination with the simulation results, and the current applied by the infrared cage is recorded. When the test officially starts, the infrared cage is controlled with a fixed current to apply the corresponding heat flow, avoiding the deviation caused by the influence of the surrounding environment on the heat flow meter 230 introduced by the closed-loop temperature control method of the heat flow meter 230. The control method for applying heat flow to the infrared cage is to set the target temperature of the heat flow meter to achieve closed-loop control. After calibration, it can be achieved by directly applying current, avoiding the deviation caused by the influence of the surrounding environment on the temperature of the heat flow meter.

[0080] In summary, the above embodiments describe in detail different configurations of thermal test fixtures and test methods for satellite-borne laser communication terminals. Of course, the present invention includes but is not limited to the configurations listed in the above embodiments. Any content that is transformed based on the configurations provided in the above embodiments belongs to the scope of protection of the present invention. Those skilled in the art can draw inferences based on the contents of the above embodiments.

[0081] In this specification, each embodiment is described in a progressive manner, and each embodiment focuses on the differences from other embodiments. The same or similar parts between the embodiments can be referred to each other. For the system disclosed in the embodiment, since it corresponds to the method disclosed in the embodiment, the description is relatively simple, and the relevant parts can be referred to the method part.

[0082] The above description is only a description of the preferred embodiments of the present invention, and is not intended to limit the scope of the present invention. Any changes or modifications made by a person skilled in the art in the field of the present invention based on the above disclosure shall fall within the scope of protection of the claims.

Claims

1. A thermal test fixture for a satellite-borne laser communication terminal, characterized in that: include: A first heat flow simulation module is configured to directly apply heat flow to the bearing component of the satellite-borne laser communication terminal; A second heat flow simulation module is configured to indirectly apply heat flow to the filter of the satellite-borne laser communication terminal; and A support system, configured to support the satellite-borne laser communication terminal and the second heat flow simulation module, and to fix the first heat flow simulation module; The main structure of the satellite-borne laser communication terminal and the first heat flow simulation module perform contact heat flow simulation, the surface of the satellite-borne laser communication terminal is wrapped with a multi-layer component, a heating loop is attached to the inner surface of the outermost layer of the multi-layer component to simulate the heat flow outside the space, and the simulation power is determined in combination with the simulation analysis; The optical filter of the satellite-borne laser communication terminal and the second heat flow simulation module perform non-contact heat flow simulation, and the heat flux density absorbed by the optical filter is determined by combining simulation analysis; wherein the distance between the second heat flow simulation module and the filter is determined according to the heat flow density absorbed by the filter; The relationship between the heat flux density applied by the second heat flux simulation module and the temperature of the heat flux meter is determined according to the distance between the second heat flux simulation module and the filter.

2. The thermal test fixture for a satellite-borne laser communication terminal according to claim 1, characterized in that: The support system comprises a tooling plate and a support structure, wherein: The tooling plate is horizontally fixed on the guide rail through a supporting structure; The satellite-borne laser communication terminal is placed horizontally and fixed on the tooling plate; A level adjustment device is provided between the tooling plate and the supporting structure for adjusting the levelness of the tooling plate.

3. The thermal test fixture for a satellite-borne laser communication terminal according to claim 2, characterized in that: The first heat flow simulation module includes a heating unit and a temperature measurement unit, wherein: The heating unit is attached to the bottom surface of the tooling plate facing the guide rail, and the temperature measuring unit and the heating unit are arranged alternately; A glass fiber reinforced plastic heat-insulating pad is provided between the tooling plate and the support structure to prevent the heat of the heating unit from leaking to the support structure through the tooling plate, and to prevent the heating unit from leaking electricity to the support structure through the tooling plate; The heating unit and the temperature measuring unit maintain the interface temperature between the satellite-borne laser communication terminal and the mounting surface of the tooling plate.

4. The thermal test fixture for a satellite-borne laser communication terminal as claimed in claim 3, characterized in that: The support system includes a lateral adjustment mounting hole and a support rod, wherein: The lateral adjustment mounting hole is located on the tooling plate and corresponds to the position of the satellite-borne laser communication terminal; The support rod passes through the transverse adjustment mounting hole and is fixed at the connection with the transverse adjustment mounting hole.

5. The thermal test fixture for a satellite-borne laser communication terminal as claimed in claim 4, characterized in that: The second heat flow simulation module includes an infrared cage and a heat flow meter, wherein: The infrared cage is fixed to the end rod of the support rod and faces the filter; The heat flow meter is arranged on a side of the infrared cage facing away from the filter; The end rod of the support rod has the functions of lateral and 360° rotation adjustment; Both sides of the infrared cage resistance wire are coated with black paint to increase the surface infrared emissivity.

6. The thermal test fixture for a satellite-borne laser communication terminal according to claim 5, characterized in that: The support rod includes a longitudinal adjustment device, a heat flow meter adjustment device, and a lateral and rotational adjustment device, wherein: The longitudinal adjustment device is used to adjust the support rod according to the height of the satellite-borne laser communication terminal; The lateral and rotational adjustment device is used to adjust the infrared cage to align with the lens barrel of the satellite-borne laser communication terminal in a lateral position according to its direction, and then rotate it to a suitable angle so that the infrared cage is parallel to and directly faces the filter; The heat flux meter adjustment device is used to adjust the position of the heat flux meter so that the distance between the heat flux meter and the filter is consistent with the distance between the heat flux meter and the infrared cage.

7. A test method based on the thermal test fixture of a satellite-borne laser communication terminal as claimed in claim 1, characterized in that: The main structure of the satellite-borne laser communication terminal and the first heat flow simulation module are subjected to contact heat flow simulation. The surface of the satellite-borne laser communication terminal is wrapped with a multi-layer component. A heating loop is attached to the inner surface of the outermost layer of the multi-layer component to simulate the heat flow outside the space. The simulation power is determined in combination with the simulation analysis. The optical filter of the satellite-borne laser communication terminal and the second heat flow simulation module perform non-contact heat flow simulation, and the heat flux density absorbed by the optical filter is determined by combining simulation analysis; Determine the distance between the second heat flow simulation module and the filter according to the heat flow density absorbed by the filter; The relationship between the heat flux density applied by the second heat flux simulation module and the temperature of the heat flux meter is determined according to the distance between the second heat flux simulation module and the filter.

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